Brake for aeroplanes



w. E. KARNES. BRAKE FOR AEROPLANES.

APPLICATION FILED OCT. 23.19I9- 1,356,289. Patented Oct. 19, 1920.

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WITNESSES INVENTOR Z1! lijifazmea, m u

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A TTORNEYS W. E. KARNES.

BRAKE FOR AEROPLANES.

APPLICATION FILED OCT. 23, 1919.

Patented Oct. 19, 1920.

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8 s S E w W ATTORNEYS WILLIAM EDWABD KARNES, OEABLINGTON, NEW JERSEY.

BRAKE FOR AEROPLANES.

specification ot Letters Iatent.

Patented Oct. 19,1920.

Application filed October 28, 1919. Serial No. 332,654.

To all whom it concern Be it known that I, WILLIAM EDWARD Kannns, a citizen of the United States, and

a resident of'Arlington, inthe county of Hudson andSt'ate of New Jersey, have mvented certain new' and useful Improve ments in Brakes for Aeroplanes, of which the following isa specification.

My said invention relates to aeroplanes and more particularlyto a means for retard-' ing the travel of the machine.

The main object of the invention is to quickly reducethe speed of an aeroplane in order to avoid collision while in the air, or to bring the machine to a stag after having traveled only a very short istance along the ground. I accomplish this result in ya ver simple manner by means of a device which is easily operated by the aviator and which is at all t mes under his control.

My invention is fully described in the following s ecification and particularly pointed out in the appended claims, reference being. had to the accompan in drawings forming a part thereof, in wlli in'the several views.

Figure 1 is a perspective view. of an aeroplane provided with my invention.

Fig. 2 is a detail perspective view of my invention detached rom the aeroplane.

Fig. 3 is a horizontal sectional view taken through one portion of the device, showing the gates closed.

Fig. 4 is a similar view with the gates partly open.

Fig. 5 is a 5-5 of Fi 2. v r

In the d fawings the letter A represents an aeroplane which I'. have shown in the I 0 n detail cross-section on the line form of a bi-plane, butwhich may be of any type of heavier-than-air machine. Secured tothe tail-portion of the fuselage isa' frame 10 comprising horizontal beams 11 and 12 connectedat their ends .b means of short vertical beams 13 and 14,1: ereby formi111 g a long, narrow rectangular structure.

. oted adjacent to the endsof the frame 10 and in the beams 11 andi12'are a series of I vertical shafts 15 provided at their u per ends with cranks 16. Fixed on each of t ese vertical shafts 15 are gates or blades 17 1 "w ch are designed to slightly overlap when n, their closed position, thereby entirely 'o erate the controllin '0 like characters of reference designate similar parts prising closing their respective portions of frame 10. Each series of shafts with their respective crank-arms are connected together by means .of a connecting rod 18 which-runs toward the center of the frame 10 and is there con- I which runs forward to the cock-pit where it is connected to an operating'lever 22 mounted within easy reach of the aviator. t

- It will be readily seen that when the aeroplane is in flight and the blades or gates are 1n their open position, the speed of the aeroplane is not in any way retarded; but, should the aviator see that he is in danger of colliding or for any reason find it neces sary to slow up the machine, he need only levers 22 to close the b ades or gates 17 WhlCh; will offer 'sufiicient resistance .to the air to cause the machine to "appreciably slow up; Also, when the aviator desires to land in a field in which there is not sufiicient distance for the mai the machine to come to a stand-still after having traveled only a very short distance.

described my said invention, what I e aim as new and desire to secure by Letters Patent is:

Havin thus 1. A device for retarding the speed'of an aeroplane, comprising an open frame straddling and connected to the trailing end thereof and vertically pivoted means for closing the space. within said frame, substantiall as set forth.

2. A evice of the class described, comprising an open rectangular frame straddling and secured at its central portion on the trailing end of the body of an aeroplane, a series of vertically disposed spaced crank shafts mounted within said frame, transversely of the body of the aero lane, blades secured to each of said crank-s afts within said frame, the vertical ends of said blades adapted to overlap, and meansto revolve said crank-shafts, substantially as set forth.

3. A device of the class described coman open frame straddling and mounted on the fuselage of an aeroplane and he free end of the bell-crank a This bell-crank projecting transversely at ri ht angles operating levers connected to the opposite thereto, a series of overlapping lades pivarm of each last mentioned bell-crank lever. otglly mgunted wiltzhifi said frame each on a3 substantially as set forth. in e en ent cran -s a a connectin ro co'nn ected to the crank arms of each geries WILLIAM EDWARD KARNES' of crank-shafts, and a bell-crank lever con- Witness:

nected to each of said connecting rods and MONTAGUE A. CLARK. 

